Nickel base alloy containing hafnium

ABSTRACT

The nickel base, cobalt containing alloys of this invention contain relatively small, but nonetheless significant, amounts of tungsten and molybdenum for solid solution strengthening, chromium for oxidation and sulfidation resistance, tantalum for solid solution and carbide strengthening, aluminum and titanium to enhance the strength by precipitation of a fine dispersed phase, gamma prime Ni3(A1, Ti), and hafnium for intermediate strength, ductility and improved oxidation resistance.

United States Patent 191 Dalai et al.

[451 Apr. 30, 1974 NICKEL BASE ALLOY CONTAINING HAFNIUM [75] Inventors: Ranes P. Dalai, Stratford; Jeremy J. Walters, Trumbull; Bruce A. Ewing,

Shelton, all of Conn.

[73] Assignee: Avco Corporation, Stratford, Conn.

[22] Filed: Apr. 12, 1972 [21] Appl. No.: 243,418

Related U.S. Application Data [63] Continuation-impart of Ser. No. 189,733, Oct. 15,

1971, abandoned.

[52] US. Cl. 75/171, 148/325 [51] Int. Cl. C22c 19/00 [58] Field of Search 75/171, 170; 148/32, 32.5

[56] References Cited UNITED STATES PATENTS 3,677,331 7/1972 Lund et al. 75/l7l 3,677,747 7/1972 Lund et al. 75/l71 Primary ExaminerRichard 0. Dean Attorney, Agent, or Firm-Charles M. Hogan; Irwin P. Garfinkle I [57] ABSTRACT .7 Claims, No Drawings 1, NICKEL BAsB' ALLoY CONTAINING HAFNIUM This application is a continuation-in-part'of our U.S. Pat. application Ser. No. 189,733, filed Oct. 15,1971,

Q A still more preferred range of compositions is as follows (in weight percent):

Balance Ni y c 0.10-0.22 Hf 0.75-1.25 now 5 Cl 12.2 13.5 Ti 3.9-4.2

This invention relates to mckel base alloys exhibiting o 85.95 Al 3.2 3.6 high strength, stability, ductility and resistance to corgig- M 331 rosion, sulfidation and oxidation at elevated tempera- Ta j tures and which are useful for blades, vanes and intebalance Ni grally cast turbine wheels. 10

The nickel base alloys of this invention contain rela- Exemplary alloys aCCOTdanF? Wlth the ieflchmgs of ti l ll, b nonetheiess i ifi amountslof this invention had the compositions shown in Table l tungsten and molybdenum-for solidsolution strength. YYMEEIQUQWS TABLE 1 Heat No. c Cr Co ivic w T6 Hf Ti Al -Ti+Al B Zl' Ni I .15 12.50 9.35 1.94 3.99 3.86 1.10 3.96 3.57 7.53 .015 .17 B61 11 .15 12.50 9.35 1.94 3.99 3.86 2.28 3.96 3.57 7.53 .015 .21 B61 111 .23 12.80 8.68 1.97 4.00 3.77 0.49 4.32 3.28 7.60 .016 .13 B61 iv .23 12.38 8.68 1.97 4.00 3.77 1.07 4.32 3.28 7.60 .016 .16 B61 v .23 12.38 8.68 1.97 4.00 3.77 1.55 4.32 3.28 7.60 .016 .14 B61 v1 .23 12.38 8.68 1.97 4.00 3.77 1.80 4.32 3.28 7.60 .016 .20 B61 v11 .23 12.38 8.68 1.97 4.00 3.77 0.44 4.32 3.28 7.60 .016 .14 B61 VH1 .20 12.31 9.18 1.94 3.72 4.05 1.06 4.08 3.38 7.46 .014 .15 B61 126 .20 12.31 9.18 1.94 3.72 4.05 2.26 4.08 3.38 7.46 .014 .22 B61 X .20 12.31 9.18 1.94 3.72 4.05 2.16 4.08 3.38 7.46 .014 .21 B61 XI .20 12.31 9.18 1.94 3.72 4.05 1.16 4.08 3.38 7.46 .014 .16 B61 X11 .19 12.66 9.42 1.92 3.75 3.86 2.40 4.01 3.27 7.28 .015 .22 861 X111 .15 12.50 8.88 2.04 3.95 5.0 1.13 3.96 3.22 7.18- .013 .10 B61 X1v .15 12.50 8.88 2.04 3.95 6.0 1.13 3.96 3.22 7.18 .013 .10 B61 Xv .20 13.35 8.88 1.91 3.87 8.0 1.20 4.18 3.21 7.39 .012 .11 B61 Xv1 .20 13.35 10.88 1.91 3.87 6.0 1.20 4.18 3.21 7.39 .012 .11 B61 xv11 .20 13.35 10.88 1.91 3.87 7.0 1.20 4.18 3.21 7.39 .012 .11 B61 xv111 .20 13.35 10.88 1.91 3.87 8.0 1.20 4.18 3.21 7.39 .012 .11 B61 XIX .15 12.87 9.49 2.01 4.01 4.0 1.05 4.10 3.23 7.33 .013 .11 B61 XX .15 12.87 9.49 2.01 5.01 7.50 1.05 4.10 3.23 7.33 .013 .11 B61 XXI .15 12.87 9.49 2.01 7.50 5.0 1.05 4.10 3.23 7.33 .013 .11 B61 XX." .15 12.87 9.49 2.01 10.0 5.0 1.05 4.10 3.23 7.33 .013 .11 B61 XX111 .16 12.60 9.40 2.0 3.97 3.85 0.50 4.0 3.55 7.55 .020 .10 B61 xxiv .21 12.80 9.40 2.19 4.0 4.08 1.95 4.05 3.25 7.30 .014 .10 B61 XXv .21 1 12.80 9.40 2.19 4.0 4.08 1.95 4.05 3.25 7.30 0.14 .15 B61 MW .21 12.80 9.40 2.19 4.0 4.08 1.95 4.05 3.25 7.30 .014 .20 B61 xxvii .09 12.30 9.10 1.87 7.40 4.94 1.25 4.18 3.35 7.53 .012 .12 B61 XXv111 .09 12.30 9.10 1.87 4.90 4.94 1.25 4.18 3.35 7.53 .012 .12 B61 XXIX .27 12.40 9.00 1.87 7.40 4.90 1.15 4.06 3.20 7.26 .013 .11 B61 ening; chromium for oxidation and sulfidation resis- After vacuum melting, the alloys noted above were tance; tantalum for solid solution and carbide strengthvacuum cast into test bars and subjected to stress rupening; aluminum and titanium to enhance the strength ture testing according to ASTM Standard E139. The by precipitation of a fine dispersed phase, gamma test bars were heat treated before testing as follows: prime Ni (Al, Ti), and hafnium for intermediate heated to'2,050 F, held at that temperature for 2 hours strength, ductility and improved oxidation resistance. then air cooled, then reheated to l,550 F and held at Compositions of the following analyses are conteml,550 F for 4 hours, then air cooled, then reheated to 'plated'as within the scope of the present invention the l,400 F and held at that temperature for 16 hours then compositions being expressed in weight percent, the air cooled; balance being Ni except for incidental impurities: After the heat treatment described above, stress rupture tests were conducted on cast test bars representative' of each of the heats in the heat treated condition g ff? g ;f ggj 5 at 1,400 F/90Ksi, 1,400 F/lOOKsi, 1,700" F/39Ksi 666 C0 8-12 Al 34 1,8.00 F/29Ksi. The results are given in Table II, it

$ gig 5 N 6 025 being noted that thickwall data refers to 0.250 inch di- Ta Zr 01 4 ameter solid .test bar results. Thinwall data refers to tubalance Ni bular test bar results in which wall thickness is 0.040

r 1 inch. Thickwall or solid test bar data reflects mechani- A m re p f r d a g f c mp i n is as f ll ws: cal property capability of heavy sections such as might c .25 max. 11f 044 be represented by turbine blade roots. Thin wall or tu- :4 17:71.5 2 54-45 bular test bar properties reflect the mechanical prop- Mc 1-2.5 Ti Al 74; erty capabilities of thin walled sections such as might 3' 8 g 8%?3 be represented by cored or hollow turbine blade air fQilS. Thinwall 6666 616 for tests 61 1,700 F/35K5l.

5 5 6 MAR-M g] is reported to be an alloy with a no elevated temperature and consisting essentially of the nal composlt or of II I I following in weight percent:

or C0 M0 w Cb Ti Al Zr B I Ni 0.15 15.8 9.5 2.0 A I 3.8 2.0 1.8 4.3 0.05 0.015 Balance INCO [N792 is reported to be the alloy described in C 30 max us. Pat. No. 3,619,182. g; $13 Table lllpresents the room temperature tensile prop- M0 1-2.5 erties of the alloy of this invention, heat treated as bea 31 fore, after casting into test bars. I Hf 0.1-3

.. 3I5 4I5 Al 3.2-3.6 TH-Al 7-8 TABLE B 0005-0025 I I Zr .05-.40 c103 ROOM TEMPERATURE TENSILE I M IBalance I TEST RESULTS I 2. A nlckel base alloy exh1b1t1ng h1gh strength, duct1l- I ity, sulfidation and oxidation resistance and stability at Hear 0 elevated temperature and consisting essentially of the 0 -S-(Ksi) E (M R- following in weight percent: I v111 1 181.4 169.2 3.5 3.2 C max 1 172.5 163.9 3.5 3.2 Cr 11-13 5 Co 8-l0 1NCo-713c 123 106 7.9 11.6 Mo 1-2.5

MAR-M421 150 130 3.5 5 Ta 3.5-5

. Hf 0.4-3.0 7 T Ti 3.5-4.5

Al Comparable values for the same commerclal alloys THAI g 3 6 are appended to the table for comparison. g (31 )05 025 In the Tables IV and V respectively, data is presented N I g' I I I v o v a e 0 cychc l test results f gg F 3. A nlckel-base alloy exh1b1t1ng high strength, duct1lt" colros'on test conducte I I I ity, sulfidation and oxidation resistance and stability at elevated temperature and consisting essentially of the following in weight percent: TABLE IV C 1042 I I Cl 12.20-13.00 COMPARATIVE c103 CYCLIC C9 8.50-9.50 Mo 1.85-2.05 OXIDATION TEST RES LTS I I I w 165405 Material Weight Change (Mg/Cm) I? After 240 Hours at 1750F 390-420 Heat v111 Egg Al 3:20-3:60 Heat IX MAR-M421 Zr 0.08-0.25

III I I II II A Ni Balance 4. A nickel base allo exhibitin hi h stren th, duea a e 1 r g g e u t1l1t sulfidatlon and ox1dat1on resistance and stabiht y I Q y at elevated tern erature and consistm essent1all of TABLE V I I P I g Y II the following 1n welght percent: COMPARATIVE c103 HOT CORROSION TEST RESULTS g 3 5 Material Depth of Attack (Mils) After f f'ggf 150 Hours at 1650F with w 365-8 6 ppm sttlt 'ra 365-8 Heat v111 4.2 Ht 075-1 25 [NCO 713C 'li 3.9-4.2 MAR-M42! 4 Al 3 24.6

- Ti+Al 7 25-770 B 0 ole-0.020 It is not intended that the invention sought to be pa- 33233 tented be hunted by the foregomg descnptlon but I 5. A nickel base alloy according to clairn l which has 111 y the 9?? f Fh p n l been heat treated to produce a desired morphology of carbides and gamma prime. I I 5 6. An article formed of the alloy of claim 1.

l. Anickel base alloy exhibiting high strength, ductil- 7. A vacuum cast article consisting of the alloy of ity, sulfidation and oxidation resistance and stability at clai 1,

We l i mg? UNITED S'IA'IES PATENT OFFICE CER'LIFICNIE 01* CORRECTION Patent a 7,993 Dated April 30, L974 Invehtofls) Ranes P. Dalal Jeremy J. Waiters, Bruce A. Ewing It is certified that error appears in the above identificd patent and that said Letters Patent are hereby corrected as shown below:

Item 19 Daiai et al. should read Dalal et al.

Item 75 Ranes P. Dalai should read Ranes P. Daiai Table II, under THICKWALL, the heading l700F/29Ksi should read l700F/39Ksi Signed and sealed this 27th day of August 1974.

LSEAL) Attest:

YMCCOY GIBSON, JR. c. MARSHALL DANN Attesting Office-r Commissioner of Patents 

2. A nickel base alloy exhibiting high strength, ductility, sulfidation and oxidation resistance and stability at elevated temperature and consisting essentially of the following in weight percent:
 3. A nickel base alloy exhibiting high strength, ductility, sulfidation and oxidation resistance and stability at elevated temperature and consisting essentially of the following in weight percent:
 4. A nickel base alloy exhibiting, high strength, ductility, sulfidation and oxidation resistance and stability at elevated temperature and consisting essentially of the following in weight percent:
 5. A nickel base alloy according to claim 1 which has been heat treated to produce a desired morphology of carbides and gamma prime.
 6. An article formed of the alloy of claim
 1. 7. A vacuum cast article consisting of the alloy of claim
 1. 